As one of the core components of an aero-engine, turbine blades operate in high temperature, high pressure, strong vibration, and other multi-physical field coupling for long periods of time. Hence, the stability of its manufacturing and service process has a direct impact on the service life of the entire engine. In this study, the design of an endoscopic probe with high resolution, small diameter, and wide temperature range is proposed. Coupled with traditional digital image correlation methods, it enables non-contact synchronous measurement of stress and temperature fields of engine blades during operation. This system features a design incorporating multiple coaxial optical paths, with a front-end optical aperture of less than 10 mm and an image plane size exceeding 25 mm. At a cut-off frequency of 40 lp/mm, the modulation transfer function exceeds 0.4 within 70% of the maximum field of view, and the maximum distortion is less than 0.1%. After undergoing non-thermalization design, this system can produce clear images within the temperature range of 20?250 ℃. The design is equally informative for other non-contact measurements in high-temperature environments.